Method of engine starting in a gas turbine engine

ABSTRACT

A method of engine starting in a gas turbine engine comprises rotating the engine to provide an air flow into a combustor of the engine and injecting fuel into the combustor at a varying rate until the engine is lighted-off. The varying rate of the fuel flow is a function of time and is represented by a curve having at least one high frequency with respect to a light-off time, representing instant changes of the rate for intersecting a light-off zone while reducing a quantity of fuel injected into the combustor. After the light-off occurrence fuel is continuously injected into the combustor to accelerate the engine to a self-sustaining operation condition. This method of the present invention is adapted to find light-off points under various temperature and altitude conditions, thereby advantageously providing a rapid light-off, particularly under cold weather conditions.

FIELD OF THE INVENTION

This invention relates to the general field of gas turbine engines andmore particularly, to a method of achieving light-off fuel flow under avariety of altitude and temperature conditions.

BACKGROUND OF THE INVENTION

In a gas turbine engine, inlet air is continuously compressed, mixedwith fuel in an inflammable proportion, and then exposed to an ignitionsource to ignite the mixture which will then continue to burn in orderto generate the combustion product.

The starting of a gas turbine engine is a complex process and generallyincludes two stages. In the first stage, the gas turbine engine isrotated by a torque provided by an external source, for example, by astarter. When a predetermined compressor pressure or speed is reached,fuel flow is injected at a controlled rate into the combustor to mixwith the air flow and the mixture is exposed to an ignition source andeventually ignition occurs. In the second stage the fuel flow iscontinuously injected into the combustor, enabling the local ignition topropagate and spread in order to form stable combustion in thecombustor. During the second stage, the engine speed is accelerated byincreasing the fuel flow injection until the engine operates under aself-sustained speed.

As part of engine design testing procedures, gas turbine engines must beable to start under conditions involving a range of temperatures andaltitudes. Altitudes can vary from as low as a few thousand feet belowsea level to altitudes that are greater than 65,000 ft. above sea level.Temperatures can range from −60 degrees F. to +135 degrees F.

The typical engine fuel control will provide a fixed starting fuel flowfor light-off based on the ambient pressure and ambient temperature. Inthe case of in-flight re-lights, the effects of ram may also be inputinto the fuel control system in order to further bias the fuel flow forlight-off.

The engine's requirements for light-off fuel delivery vary significantlywith engine size, the number of nozzles, the type of nozzles used, thealtitude, the temperature of the air and fuel, the viscous andaerodynamic drag effects on the rotors and the forward velocity of theengine. Increasing altitude causes a rarefying of the air and a need toreduce the light-off fuel flow. Very cold temperatures cause a need forhigher fuel flows in order to achieve light-off. In particular, at verycold, high altitude static starts, a high light-off fuel flowrequirement may be needed in order to initiate light-off. However,sustaining this flow may result in overtemperatures in the turbine areaand the associated stresses that follow. In addition, this high fuelflow required for light-off may lead to visual flame being emitted fromthe jet pipe or exhaust of the engine. Longer light-off times may resultin fuel pooling. Once this pooled fuel finally burns, visible torchingmay result. This torching is highly undesirable as it may also lead toengine distress on the turbine blading.

Efforts have been made in the industry to improve gas turbine enginestarting, particularly for reducing light-off time which is taken fromthe point of fuel injection to the light-off occurrence, in order tohave a quick start-up of the engine. U.S. Pat. No. 5,718,111, issued toLing et al. on Feb. 17, 1998, as an example of such efforts, describes agas turbine engine start-up control system and method in which theengine exit temperature and the compressor speed change rate are sensed,and the sensed parameters are compared with desired start-upcharacteristics and referenced to look-up tables for determining anoutput composition factor. Based on the output composition factor, thestart-up of the gas turbine engine is adjusted, generally by adjustingfuel flow through use of a fuel control system. However, this method andsystem are generally used for controlling fuel flow in the second stageof engine start-up because the engine exit temperature changes after thelight-off occurrence.

U.S. Pat. No. 6,062,016, issued to Edelman on May 16, 2000 discloses agas turbine engine light-off system and method in which the gas turbineengine is operated at a fixed speed in order to provide a substantiallyconstant supply of combustion air for light-off, and the fuel flow isramped up to achieve the correct fuel-to-air ratio for light-off.

U.S. Pat. No. 5,107,674, issued to Wibbelsman et al. on Apr 28, 1992describes a starting system for a gas turbine aircraft engine. Thestarting system automatically controls the sequencing of events neededduring engine start-up that lead up to light-off, including sensors forambient temperature, exhaust gas temperature, compressor speed, fuelflow, etc. The control schedules fuel flow in a manner which avoidsstalls and takes corrective action when stalls occur, and providesscheduling of fuel flow in severely cold conditions.

U.S. Pat. No. 5,369,948, issued to Vertens et al. on Dec. 6, 1994describes a process and apparatus for starting a gas turbine engine. Inthis apparatus with a start-up controller for a gas turbine engine, theamount of fuel injected by controlled dosing pumps is determined,whereby the amount of fuel injected can be regulated as a function ofthe difference between the injection pressure and the compressorpressure in the combustion chamber of the turbine, or at the compressoroutlet.

Nevertheless, there is still a need for a better engine starting methodfor reducing light-off time of engine start-up and for avoidinginjection of excess fuel during engine start-up, particularly under coldweather conditions because the fuel accuracy of achieving light-off ofgas turbine engines becomes more critical as the fuel and airtemperature get colder.

SUMMARY OF THE INVENTION

A method of engine starting in a gas turbine engine according to oneaspect of the present invention comprises steps of rotating the engineto provide an air flow into a combustor of the engine, and injectingfuel into the combustor at a varying rate until the engine islighted-off. The varying rate of fuel injection is a function of timeand is represented by a curve having at least one high frequency whichrepresents instant changes of the rate for intersecting a light-offzone. The curve preferably further has a low frequency with respect tothe light-off time, representing a change trend of the varying rate.After the light-off occurrence the engine is accelerated to a selfsustaining operation condition by continuously injecting fuel into thecombustor. The engine may be rotated at a varying speed as a function oftime, such as an increasing speed, or rotated at a fixed speed, in orderto achieve light-off. The curve for intersecting a light-off zonepreferably has an increasing trend and comprises, for example, anoscillatory profile, a squared-off wave profile, a step profile or aseries of spikes, according to various embodiments.

The mixture of fuel and air can be ignited, which is generally referredto as light-off, in the combustor of a gas turbine engine with afuel/air ratio falling within an appropriate range. This fuel/air ratiorange for light-off is affected by fuel viscosity, atmospherictemperature, and atmospheric air pressure. The air pressure is primarilydetermined by the compressor speed and the altitude where the gasturbine engine is positioned. During gas turbine operation, includingthe start up procedure thereof, the air flow entering the combustor andmixing with the fuel is driven by the engine compressor, and thereby theair flow rate is a function of the compressor speed or the engine speed.Thus, the fuel/air ratio range for light-off is primarily determined bya light-off zone of a fuel flow rate and an engine speed rate. Thelight-off zone is affected by the atmospheric temperature and thealtitude where the engine is positioned. This will be further discussedhereinafter. Therefore, it is usually difficult to achieve a quicklight-off under various temperature and altitude conditions,particularly in cold weather unless the precise light-off zone can beidentified under those conditions.

In contrast to the conventional manner of fuel injection for light-off,in which the fuel injection rate is generally represented by a linear ormonotonic curve, the present invention provides a novel manner ofinjecting fuel into the combustor for achieving light-off in which fuelis injected at a varying rate which can be represented by a curve havingat least one high frequency, for example, an oscillatory profilerepresenting instant changes of the rate providing various instantfuel/air ratios in order to locate the light-off zone associated withthe specific temperature and altitude conditions while reducing thequantity of fuel injected into the combustor. This will be furtherdiscussed with reference to the drawings and embodiments hereinafter.

In one embodiment of the present invention, a plurality of sensors areprovided to measure the temperatures of the fuel and air flow to beinjected into the combustor, the forward flight velocity ram quantitywhich is measured as the pressure difference between the inlet andoutlet of the gas turbine engine, and the speed of the engine. Themeasured data is processed to determine a minimum engine speed at whichthe introduction of a predetermined first fuel flow level begins. Thetemperature of the exhaust gas flow is also measured to determine iflight-off occurs. The light-off time is measured and stored in adatabase along with all other measurement data for reference in a futurelight-off of the gas turbine engine occurring under similar altitude andtemperature conditions. Thus, the predetermined first fuel flow level,the criteria for the minimum engine speed for the introduction of thepredetermined first fuel flow level, and the profile of the curverepresenting the varying fuel injection rate can be adjusted to achievea shorter light-off time based on the information stored in thedatabase.

The foundation of the present invention is based in part on theprinciple that “at any given air mass flow, the range of air/fuel ratiowithin which the mixture can be ignited is smaller than that for whichstable combustion is possible once ignition has occurred”. Thisprinciple is stated in “Gas Turbine Theory by H. Cohen, G. F. C. Rogersand H. I. H. Saravanamuttoo”. The increasingly oscillatory light-offfuel flow will intersect the light-off zone and once the engine islighted-off, the combustion will be sustained at a lower fuel flowbecause light-off of the fuel/air mixture occurs at a particular momentwithin a very small local area such that a light-off occurrence isprimarily determined by the instant fuel/air ratio, or by the instantfuel flow rate. On the other hand, stable combustion is more effectivelydetermined by the average fuel/air ratio or by the average fuel flowrate. The average fuel flow of every cycle of the light-off fuel flow islower than the maximum fuel flow rate in the same cycle. Thus, quicklight-off of a gas turbine engine can be achieved and continuouscombustion can be sustained even in very cold weather, and excess fuelinjection can thereby be avoided.

Other advantages and features of the present invention will be betterunderstood with reference to preferred embodiments and drawings of thepresent invention described hereinafter.

BRIEF DESCRIPTION OF THE DRAWINGS

Having thus generally described the nature of the present invention,reference will now be made to the accompanying drawings, showing by wayof illustration the preferred embodiments thereof, in which:

FIG. 1 is a cross-sectional view of a gas turbine engine incorporating apreferred embodiment of the present invention;

FIG. 2 is a simplified diagram illustrating an engine starting methodaccording to the embodiment of FIG. 1;

FIG. 3 is a graphical representation showing a fuel injection profileused in the embodiment of FIG. 1;

FIG. 3 a is a graphical representation showing the details of the fuelinjection profile of FIG. 3;

FIGS. 3 b-3 d are graphical representations showing various fuel flowprofiles according to various embodiments of the present invention;

FIG. 4 is a graphical representation showing a light-off zone defined bythe fuel flow rate and the engine rotational speed rate;

FIG. 5 is a schematic representation, showing changes of a light-offzone affected by temperatures and altitudes; and

FIG. 6 is a geographical representation showing a fuel flow intersectinga light-off zone according to one embodiment of the present invention.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

Referring to the drawings, particularly FIG. 1, an exemplary gas turbineengine 10 includes in serial flow communication about a longitudinalcenterline axis 12, a fan having a plurality of circumferentially spacedapart fan or rotor blades 14, a conventional low pressure compressor 16,a conventional high pressure compressor 18, a conventional annularcombustor 20, a conventional high pressure turbine 22 and a conventionallow pressure turbine 24. The low pressure turbine 24 is securelyconnected to both the low pressure compressor 16 and the fan blades 14by a first rotor shaft 26, and the high pressure turbine 22 is securelyconnected to the high pressure compressor 18 by a second rotor shaft 28.Conventional fuel injection means 30 are provided for selectivelyinjecting fuel flow into the combustor 20 for powering the engine 10. Aspark igniter 33 is provided in the combustor 20 in close proximity tothe fuel nozzles (not indicated by numerals) of the fuel injection means30.

A conventional annular casing 32 surrounds the engine 10 from the lowpressure compressor 16 to the low pressure turbine 24 and defines, withthe low pressure compressor 16, a low pressure compressor inlet 34 forreceiving a portion of ambient air represented by arrows 36. Thedownstream end of the casing 32 defines with a conventional annularexhaust plug 40, an annular exhaust outlet 42. A portion of the ambientair 36 compressed by the fan blades 14 adjacent to the blade roots 38 isfurther compressed by the low pressure compressor 16 and the highpressure compressor 18 and is forced into the combustor 20. The mixtureof the compressed air 36 and the fuel injected by the fuel injectingmeans 30 generates combustion gases represented by arrows 52. Thecombustion gases 52 cause the high pressure turbine 22 and the lowpressure turbine 24 to rotate respectively for powering the highpressure compressor 18, the low pressure compressor 16 and the fanblades 14.

Surrounding the blades 14 and the upstream portion of the casing 32 is anacelle 44 which is spaced radially outwardly from the casing 32defining with the casing 32, an annular duct 55 for permitting theradially outer portion of the air 36 compressed by the blades 14, tobypass the engine. For convenience of description this bypass air flowis indicated by arrows 36 a. A plurality of circumferentially spacedstator vanes 46 extend radially between the casing 32 and the nacelle44, and are spaced apart axially downstream from the blades 14. Thenacelle 44 includes an inlet 48 at its upstream end for receiving theambient air 36, and an outlet 50 at its downstream end for dischargingthe bypass air flow 36 a for providing a portion of thrust.

Reference will now be made to both FIGS. 1 and 2. During a start-upprocess of the engine 10, the engine 10, more particularly the highpressure compressor 18 of the engine 10 is rotated by a starter (notshown) to provide the air flow 36 into the combustor 20. A sensor (notshown) associated with the high pressure compressor 18 measures therotational speed of the high pressure compressor 18 and sends a speedsignal which is represented by block 60 to an electronic enginecontroller 56. When a minimum rotational speed of the high pressurecompressor 18 according to predetermined criteria, is reached, theelectronic engine control 56 signals the fuel injecting means 30 whichincludes the fuel pump 29 and a stepper, or torque motor valve 31, or anequivalent function valve to begin injection of a fuel flow into thecombustor which, for example, has an increasingly oscillating profile asillustrated in block 78 in which F represent Fuel Flow and T representsTime. The mixture of fuel and air having a varying fuel/air ratiocontacts the spark igniter 33, causing light-off of the combustionprocess in the combustor 20 when an appropriate fuel/air ratio isreached. In order to determine a light-off occurrence, an exhausttemperature signal represented by block 62 is sent to the electronicengine control 56 by a temperature sensor (not shown) associated withthe annular exhaust outlet 42. When a threshold temperature of 200° F.,for example, is measured, the electronic engine control 56 signals thefuel injecting means 30 to inject fuel flow according to a fuel schedulerequired for the engine operation from the light-off point to aself-sustaining condition, which is based on current known profiles.This fuel schedule could follow an open loop fuel flow profile based ona desired rate of acceleration or could be based on a limiting exhausttemperature signal 62 as pertains to a specific engine application.

During the light-off procedure, the electronic engine control 56 alsoreceives a temperature signal 64 of the ambient inlet air 36, analtitude signal 66 indicated by the altitude pressure of the inlet air,a ram signal 68 which is a measurement of the forward velocity orpressure differential existing across the engine 10, and a fueltemperature signal 70. These signals are used by the electronic enginecontrol 56 to select an appropriate fuel flow profile for the light-offprocedure. A timing signal 72 generated from a timer circuit (not shown)integrated in the electronic engine control 56 is used for measuring thelight-off time which is taken from the point of the beginning of thefuel injection to the light-off occurrence. A torching signal 74 is anoptional ultraviolet or photoelectric signal which indicates thepresence of visible flames at the exhaust outlet 42 of the engine 10. Adatabase 58 is provided with the electronic engine control 56 forstoring all data sensed or measured as well as other predetermined dataand programs.

The engine starting method is further discussed in principle and isdescribed in detail with reference to FIGS. 3-6. The fuel flow at avarying rate injected into the combustor to reach light-off is afunction of time and is represented by a curve 76, as shown with thecoordinates of flow rate (F) and time (T) in FIG. 3, having a lowerfrequency representing a change trend of the fuel flow rate and at leastone high frequency representing instant changes of the flow rate. Thetime duration between T₂ and T₁ is the light-off time where the fuelinjection begins at time T₁ and the light-off occurs at T₂.

The low frequency of the curve 76 has a cycle time duration much greaterthan the light-off time, or the time duration between T₂ and T₁ so thatthe low frequency of the curve 76 generally represents the changingaverage flow rate which filters the high frequency components and isillustrated by the broken line section of the curve 76. In thisembodiment of the present invention, the change trend of the fuel flowrate represents an increasing trend. However, the curve 76 may notnecessarily include the low frequency. With a self-learning functionincorporated into this engine starting method, a rapid light-off can beachieved without the change trend of the varying fuel flow rate. Thiswill be further described hereinafter.

The at least one high frequency curve 76 in this embodiment comprises anincreasingly oscillating profile and more particularly, comprises aseries of spikes 80 which, as more clearly illustrated in FIG. 3 a,generally include a relatively low and steady flow rate section S₁ and arapidly and instantly increasing section S₂ to reach an instant maximumflow rate Ma as well as a decreasing section S₃ representing a smoothchange of the fuel rate, instantly and rapidly decreasing from theinstant maximum flow rate Ma to a relatively low and stable flow rate ofthe next cycle of the spikes. Nevertheless, the at least one highfrequency curve 76 could vary, as represented by, for example, asquared-off profile 76 b as shown in FIG. 3 b, a generally oscillatoryprofile such as a random oscillation profile 76 c, as shown in FIG. 3 c,or a step profile 76 d as shown in FIG. 3 d.

It is noted that on one hand, light-off occurs within a very briefmoment and is generally determined by the instant fuel/air ratio, and onthe other hand, a stable combustion process generally depends on theaverage fuel/air ratio. It is a generally accepted principle that at anygiven air mass flow, the range of air/fuel ratio within which themixture can be ignited is smaller than that for which stable combustionis possible once ignition has occurred. The varying fuel raterepresented by the curve 76 having high frequency componentsadvantageously provides a plurality of instant maximum fuel flow rates,while maintaining the average flow rate at a gradually changing levelrelatively lower than those instant maximum fuel flow rates. When theair flow rate into the combustor 20 is fixed or changes in a relativelystable manner, the fuel/air ratios are determined primarily by theproperties of the curve 76. These instant maximum fuel flow rates ensurethe relative smaller air/fuel ratio for light-off, and the low averagefuel flow level ensures a relative greater air/fuel ratio for stablecombustion. Therefore, the increasingly oscillating fuel flow raterepresented by curve 76 provides a novel light-off fuel flow profilewhich meets the light-off requirements stated in this principle.

The fuel flow rate curve 76 generally includes a predetermined firstfuel flow level F₁ which is only maintained for a short period of timeand then changes to the oscillating profile. The predetermined firstfuel flow level F₁ and the beginning time T₁ of the fuel flow injectionas well as other properties of the fuel flow curve 76 are determinedaccording to the altitude and temperature conditions under which theengine 10 is started. This will be further described hereinafter.

FIG. 4 illustrates the relationship between the light-off occurrence andthe fuel flow rate as a percentage of the fuel flow rate indicated by WF(%), and gas generator speed as a percentage of a full gas generatorspeed, indicated by Ng (%). It is understood that the gas generatorspeed in FIG. 4 is equivalent to the rotational speed of the highpressure compressor 18 of the engine. In FIG. 4 the fuel flow isinjected into the combustor at varying rates, and the air flow iscompressed into the combustor at varying rates which correspond to thegas generator speed rates. Thus, varying fuel/air ratios can be obtainedand are represented as cross points by the vertical and horizontallines. Nevertheless, only those cross points representing theappropriate fuel/air ratios meet the requirements for light-off underparticular altitude and temperature conditions. These cross pointsrepresent an area defined by the closed circle B. The cross pointsrepresenting fuel/air ratios at which light-off does not occur definethe area C surrounding the area B. The light-off area B which will bereferred to as the light-off zone hereinafter, includes a range offuel/air ratios at which light-off can occur. However, the light-offtime at different fuel/air ratios is different. Generally, the light-offtimes at the fuel/air ratios represented by the cross points within thelight-off zone and close to the boundary thereof are longer than thelight-off times at the fuel/air ratios represented by the cross pointsclose to the center of the light-off zone. Thus, a central area definedby the closed circle A illustrates a smaller range of fuel/air ratiosfor a more rapid light-off.

FIG. 5 is a schematic, graphical representation showing the light-offzones under various altitude and temperature conditions in which thelight-off zones are schematically illustrated for discussion purposesonly, and are not the direct results of testing. The ambient airtemperature not only directly affects the temperature of the air flow,fuel flow and thereby the temperature of the mixture injected into thecombustor, but also affects the density of the air which thereby affectsthe actual fuel/air ratio when the fuel flow rate and the enginegenerator speed are fixed. The ambient air pressure is varied atdifferent altitudes which changes the density of the ambient air,thereby affecting the actual fuel/air ratio. Thus, the light-off zonewill change when either altitude or ambient temperature conditionschange. The light-off zones 82-92 illustrated in FIG. 5 are therespective samples of FIG. 4 under various temperature and altitudeconditions. The general effect of temperature at high altitudes on thelight-off boundary is illustrated in the high altitude cold temperaturezone 82, the high altitude moderate temperature zone 84, and the highaltitude hot temperature zone 86. The general effect of temperature atlow altitudes on the light-off boundary is illustrated in the lowaltitude cold temperature zone 88, the low altitude moderate temperaturezone 90 and the low altitude hot temperature zone 92. It is shown thatat a fixed altitude condition the light-off zone B becomes smaller andthe position of the light-off zone B with respect to the coordinates ofthe fuel flow and gas generator speed changes when the ambient airtemperature becomes colder. The light-off zone B also changes in itsshape and position when the altitude changes but the ambient airtemperature remains relatively constant. Therefore, parametersdetermining the fuel flow rate curve 76 in FIG. 3 must be changed inresponse to the changes in altitude and temperature conditions in orderto achieve a rapid light-off.

The fuel flow rate curve 76 shown in FIG. 3 is a function of time.During a start-up process, the gas generator speed gradually increasesand is also a function of time. Therefore, the varying fuel flow rate asa function of time can be changed to a function of gas generator speedby applying a mathematic calculation, and thereby the fuel flow ratecurve 76 in FIG. 3 is converted to a corresponding fuel flow rate curve76′ with reference to the coordinates fuel flow percentage WF (%) andthe gas generator speed percentage NG (%), shown in FIG. 6. Ahypothetical light-off zone 94 and its central area 96 for rapidlight-off are also shown in FIG. 6.

It will be understood that when the fuel flow rate curve 76′ intersectsthe light-off zone 94 or its central area 96, the requirements forlight-off are met and light-off occurs. However, the accurate pointwithin the hypothetical light-off zone 94 at which the light-off occursvaries, depending on the parameters of the curve 76′ and otherconditions. As illustrated in FIG. 5, the size, shape and position ofthe light-off zone vary under different altitude and temperatureconditions. Therefore, it is difficult to locate light-off under variousaltitude and temperature conditions, especially in very cold weatherbecause the light-off zone is relatively smaller. The spike profile orthe other profiles of the curve shown in FIGS. 3 b-3 d sweeps an areawhen the average fuel flow rate increases so that the curve 76′advantageously provides more possibilities to intersect the hypotheticallight-off zone or its central area 96, in contrast to a varying fuelflow rate represented by a linear or a monotonic curve which is used inprior art to intersect the light-off zone for engine combustionlight-off.

The hypothetical light-off zone 94 and its central area 96 are changedin shape, area and position when the altitude and temperature conditionsvary, and so the parameters determining the curve 76′ must be changedaccordingly. These parameters are minimum gas generator speed V₁ tobegin the engine injection and the predetermined first fuel flow levelF₁ when the fuel injection begins. The parameters also include Δ₁, Δ₂,Δ₃, Δ₄, etc. of gas generator speed increments and H₁, H₂, H₃, H₄, etc.of fuel flow increments with respect to the circles or spikes of thecurve 76′ as shown in FIG. 6. These increments may be equal, exponentialor logarithmic, depending on the results of empirical testing.Initially, the minimum gas generator speed V₁ and the first level fuelflow F₁ as well as the increments Δ and H associated with variousaltitude and temperature conditions are predetermined by empiricaltesting. During a light-off process under a specific altitude andtemperature condition, the temperature of the fuel and the temperatureof the air flow, a forward flight velocity ram quantity and an ambientair pressure, as well as the gas generator speed, are sensed. Thissensed data is sent to the electronic engine control to determine theminimum gas generator speed V₁ for the introduction of the predeterminedfirst fuel flow level F₁. The electronic engine control processes thissensed data to further select other parameters of the light-off flowrate curve 76′, such as the first fuel flow level F₁ the fuel incrementsH and the gas generator speed increments Δ from the empirical testingdata stored in the database, in order to determine an appropriateprofile of the light-off fuel flow curve 76′, thereby achieving a rapidlight-off under that particular altitude and temperature condition. Thelight-off time is then measured and that information is stored in thedatabase for future reference.

In a future light-off process, all sensed data is compared with datagenerated in previous light-off processes to determine if the dataassociated with an altitude and temperature condition similar to acurrent altitude and temperature condition exists. If the search resultis positive, then the parameters of the light-off fuel flow curve 76′used in the previous light-off process under similar altitude andtemperature condition will be used to determine the information aboutthe hypothetical light-off zone 94 and its central area 96. Based on thenewly determined information about the light-off zone 94 and its centralarea 96 under this particular altitude and temperature condition, theelectronic engine control selects new parameters of F₁, V₁, H, Δ, etc.of the light-off fuel flow curve 76′ so that the commencement point ofthe curve 76′ is closer to the hypothetical light-off zone 94 and itscentral area 96, and the profile of the curve 76′ is also better inorder to achieve a light-off occurrence. The light-off time is measuredand compared with the stored light-off time of the previous light-offprocess under the same altitude and temperature condition. If thecurrent light-off time is shorter than the previous light-off time, allthe currently sensed data are stored in the database to replace thepreviously stored data. If the current light-off time is longer than thepreviously stored light-off data, the currently sensed data is notstored. Thus, a self-learning function is incorporated into the enginestarting light-off method of the present invention. With such aself-learning function, the optimized curve 76′ may not necessarilyinclude the low frequency representing the change trend of the varyingfuel flow rate because only one or a few more cycles of the highfrequency oscillation may successfully cause the light-off occurrence.The parameters H and A of the cycles however, may vary.

It is noted that in the above described embodiment of the presentinvention, the gas generator speed increases during the light-off time.This is one example of the present invention which is convenient fordiscussion. The present invention is also applicable when the generatorspeed is fixed during the light-off time.

Modifications and improvements to the above-described embodiment of thepresent invention may become apparent to those skilled in the art. Theforegoing description is intended to be exemplary rather than limiting.For example, instead of the gas turbine engine having an annularcombustor as described in the embodiment, the present invention can beused with different types of engines such as gas turbine engines havingseparate combustion liners. The scope of the invention is thereforeintended to be limited solely by the scope of the appended claims.

1. A method of engine starting in a gas turbine engine, comprising:measuring at least one parameter of a current environment in which theengine is to be started; searching in a database for at least oneparameter regarding an engine starting process in a previous environmenthaving a parameter similar to the measured parameter; determining atleast one new -parameter for an engine starting process in the currentenvironment, based on information relating to the parameter searched inthe database; starting the engine using the new parameter and completinga current engine starting process; measuring a light-off time of theengine during the current engine starting process; and comparing themeasured light-off time with a previous light-off time stored in thedatabase and associated with the previous environment, and re-writingthe database with the new parameter and the measured light-off time whenthe measured light-off time is shorter than the previous light-off timestored in the database.
 2. The method as claimed in claim 1 wherein theat least one parameter of the current environment comprises a parameterselected from a group of following parameters: temperature, altitude andpressure difference between an engine inlet and an engine outlet.
 3. Themethod as claimed in claim 1 wherein the at least one parameter of thecurrent environment comprises temperature and altitude.
 4. The method asclaimed in claim 1 wherein the at least one parameter regarding theengine starting process comprises a parameter selected from a group offollowing parameters: a minimum fuel flow rate and a minimum compressorspeed at which a fuel flow at the rate is to be introduced for ignition.5. The method as claimed in claim 1 wherein the at least one parameterat least one parameter regarding the engine starting process comprises aminimum fuel flow rate and a fuel flow increment during the enginestarting process.
 6. The method as claimed in claim 1 wherein the atleast one parameter at least one parameter regarding the engine startingprocess comprises a minimum compressor speed at which a fuel flow at therate is to be introduced for ignition, and a compressor speed incrementduring the engine starting process.